CN110155312B - Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment - Google Patents
Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment Download PDFInfo
- Publication number
- CN110155312B CN110155312B CN201910391677.5A CN201910391677A CN110155312B CN 110155312 B CN110155312 B CN 110155312B CN 201910391677 A CN201910391677 A CN 201910391677A CN 110155312 B CN110155312 B CN 110155312B
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- framework
- battery compartment
- upper layer
- battery
- shaped metal
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- 239000000758 substrate Substances 0.000 claims abstract description 36
- 229910052751 metal Inorganic materials 0.000 claims abstract description 29
- 239000002184 metal Substances 0.000 claims abstract description 29
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 9
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 9
- 229910052802 copper Inorganic materials 0.000 claims description 9
- 239000010949 copper Substances 0.000 claims description 9
- 229910000838 Al alloy Inorganic materials 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 229910000975 Carbon steel Inorganic materials 0.000 claims description 3
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 claims description 3
- 239000010962 carbon steel Substances 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 description 5
- 238000005452 bending Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 108010066114 cabin-2 Proteins 0.000 description 1
- 230000002498 deadly effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
- Battery Mounting, Suspending (AREA)
Abstract
The invention discloses a battery compartment of a multi-rotor manned aircraft, which comprises an upper layer flip cover plate, a framework upper layer edge substrate, power distribution modules, a field-shaped metal framework, battery modules, a flight control module and a lower layer substrate, wherein the upper layer flip cover plate and the framework upper layer edge substrate are arranged on the upper surface of the field-shaped metal framework; the flight control module is fixed on the lower surface of the lower substrate. The battery compartment is firm in structure, convenient to operate and convenient to maintain.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a battery compartment of a multi-rotor manned aircraft and the manned aircraft comprising the battery compartment.
Background
The multi-rotor manned aircraft has wide application prospect in the low-altitude traffic field. The existing multi-rotor manned aircraft is mainly divided into electric drive and oil-electricity hybrid drive based on a power energy form. The electric drive multi-rotor manned aircraft has the advantages of cleanness, environmental protection, convenient maintenance and the like. The overall architecture of the electrically driven multi-rotor aircraft is indistinct from the layout of a battery compartment, and the existing architecture scheme is mainly divided into two types based on the relative positions of a cabin and a paddle plane: the cabin is above a battery compartment, the battery compartment is wrapped in a main frame, and the main frame is connected with a horn provided with a lifting assembly (a motor and a propeller), and is represented by CN 205311899U; the other is that the cabin is below the battery compartment, which is designed with the main frame, and the main frame is connected with the arm with the lift assembly, as represented by CN 206750136U. In the first type of complete machine architecture, the cabin is arranged above the battery compartment, and the system has the advantages of good maneuvering performance and control performance, and the system has the defects of great deadly potential safety hazards, such as possibility of directly striking the cabin when the propeller is shot in the air, and inconvenience of passengers escaping when the rotating speed of the propeller is out of control. In the second type of architecture, the cabin layout is below the battery compartment, and has the advantages of good stability of the aircraft attitude and high safety level, and the disadvantage of being inconvenient to take and place the battery and large in structural design difficulty.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a battery compartment of a multi-rotor manned aircraft and the manned aircraft comprising the battery compartment, and the aircraft has good mechanical property, long endurance, heavy load and better safety.
The aim of the invention is achieved by the following technical scheme:
the battery compartment of the multi-rotor manned aircraft is characterized by comprising an upper layer flip cover plate, a framework upper layer edge substrate, power distribution modules, a field-shaped metal framework, battery modules, a flight control module and a lower layer substrate, wherein the upper layer flip cover plate and the framework upper layer edge substrate are arranged on the field-shaped metal framework upper surface, the lower layer substrate is fixed on the field-shaped metal framework lower surface, the upper layer flip cover plate, the framework upper layer edge substrate, the field-shaped metal framework and the lower layer substrate enclose a four-quadrant inner space, four groups of battery modules are respectively and fixedly arranged in the four-quadrant inner space, two power distribution modules are fixedly arranged on the upper layer flip cover plate corresponding to each group of battery modules, each power distribution module is provided with conductive copper bars, the upper layer flip cover plate is rotatably connected with two sides of the field-shaped metal framework, and after the upper layer flip cover plate is turned down, the conductive copper bars can be communicated with the conductive copper bars on the power distribution modules; the flight control module is fixed on the lower surface of the lower substrate.
Further, the V-shaped metal framework is made of aluminum alloy, magnesium aluminum alloy or carbon steel.
Further, the upper layer edge substrate and the lower layer substrate are both made of carbon fiber composite materials.
Further, the field-shaped metal framework consists of a framework side plate, a framework longitudinal beam, a framework cross beam and a cross frame, wherein the framework side plate, the framework longitudinal beam, the framework cross beam and the cross frame are all detachably connected.
Further, the inner side surface of the skeleton side plate is uniformly provided with a plurality of skeleton hangers for connecting cabins.
Further, a plurality of battery mounting positions are also arranged on the inner side surfaces of the framework side plates and the cross.
The multi-rotor manned aircraft is characterized by comprising the battery compartment, a power module, a battery compartment, a cabin and an undercarriage, wherein the power module is directly connected with the battery compartment and is arranged at the same height to form a flying platform; the cabin is fixed below the battery cabin, and the landing gear is arranged at the bottom of the cabin.
The beneficial effects of the invention are as follows:
the battery compartment of the multi-rotor manned aircraft adopts the field-shaped metal framework, so that the overall structure of the battery compartment is firm, the rigidity is high, the battery module 25 can be more conveniently taken and placed through the upper cover plate which can be turned over, and the flight control module is fixed on the lower surface of the lower substrate, thereby facilitating maintenance; and the battery compartment can be directly connected with the power module, so that the length of a power cable is shortened.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a multi-rotor manned aircraft of the present invention;
FIG. 2 is a side view of the overall structure of the multi-rotor manned aircraft of the present invention;
FIG. 3 is a schematic view of the structure of the horn after being folded down;
FIG. 4 is a schematic view of the structure of a battery compartment;
FIG. 5 is a schematic view of the battery compartment after the battery cover is opened;
FIG. 6 is a schematic view of a battery compartment-shaped skeleton;
in the figure, 1-power module, 2-battery compartment, 3-cabin, 4-landing gear, 11-power component, 12-horn component, 21-upper flip cover plate, 22-framework upper edge substrate, 23-electricity distribution module, 24-field-shaped metal framework, 25-battery module, 26-flight control module, 27-lower substrate, 31-seat, 111-motor seat, 112-motor, 113-electric tuning, 114-propeller, 121-horn tube, 122-Y-shaped connecting piece, 241-framework side plate, 242-framework longitudinal beam, 243-framework cross beam, 244-cross frame, 245-framework hanging lug and 246-battery installation position
Detailed Description
The objects and effects of the present invention will become more apparent from the following detailed description of the preferred embodiments and the accompanying drawings, in which the present invention is further described in detail. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
As shown in fig. 1, the multi-rotor manned aircraft comprises four parts, namely a power module 1, a battery compartment 2, a cabin 3 and a landing gear 4, wherein the power module 1 is directly connected with the battery compartment 2 and is positioned at the same height in layout to form a flying platform; the cabin 3 is located below the battery compartment 2 and the landing gear 4 is mounted below the cabin 3. The whole machine layout ensures that the paddle plane is positioned above the cabin, thereby avoiding the damage caused by the ejection of potential paddles; meanwhile, the gravity center of the whole machine is lower than the plane of the paddle, so that the stability of the flying attitude is facilitated; in addition, the length of the power cable can be shortened, and the power cable has the advantages of modularized design, convenience in maintenance and the like.
As shown in fig. 1 and 2, the power module 1 has four power modules, which are respectively fixed at four right angles of the battery compartment 2, the power module 1 includes a power assembly 11 and a horn assembly 12, the horn assembly 12 includes a Y-shaped connecting piece 122 and two horn tubes 121 connected to two branches of the Y-shaped connecting piece 122, a set of power assembly 11 is fixed at an end of each horn tube 121, the power assembly 11 includes a motor base 111, a motor 112, an electric regulator 113 and a propeller 114, the motor base 111 is fixed at an end of the horn tube 121, the electric regulator 113 is installed inside the motor base 111, the upper end and the lower end of the motor base 111 are respectively provided with a motor 112, and each motor 112 drives one propeller 114, thereby being configured into an eight-axis sixteen-propeller form. By adopting the mode of coaxially installing two sets of motor propellers up and down at the tail end of each group of power components 11, the aircraft is enabled to bring greater lifting of the incoming endurance and the load in the limited design size range of the aircraft, and meanwhile, the safety redundancy of a power system is achieved.
To facilitate storage and transport of the aircraft, the two horn tubes 121 connected at the two prongs of the Y-connector 122 may be folded down relative to the Y-connector 122, as shown in fig. 3. When the horn is unfolded, the aircraft is in a flying state, when the horn is folded downwards, the aircraft is in a storage state, and after folding, the whole aircraft is greatly reduced in size, so that the aircraft is convenient to package and transport on the ground. The included angle between the two horn tubes 121 is related to design parameters such as the overall wheel base, the horn length, the blade diameter and the like, and the preferred angle alpha is more than or equal to 45 degrees and less than or equal to 135 degrees. In order to maintain the rigidity while satisfying the requirement for light weight, the horn tube 121 is made of a carbon fiber composite material.
The battery compartment 2 of the aircraft is directly connected with the power module 1 and the cabin 3, so that the aircraft is required to bear huge bending moment generated by the power module 1, bear the dead weight of the battery and the weight of the cabin and passengers, meet the light weight requirement of the aircraft design, and simultaneously give consideration to the operation convenience.
As shown in fig. 4-6, the battery compartment 2 includes an upper layer flip cover 21, a frame upper layer edge substrate 22, a power distribution module 23, a field-shaped metal frame 24, a battery module 25, a flight control module 26 and a lower layer substrate 27, wherein the upper layer flip cover 21 and the frame upper layer edge substrate 22 are arranged on the upper surface of the field-shaped metal frame 24, the lower layer substrate 27 is fixed on the lower surface of the field-shaped metal frame 22, the upper layer flip cover 21, the frame upper layer edge substrate 22, the field-shaped metal frame 24 and the lower layer substrate 27 enclose a four-quadrant inner space, four groups of battery modules 23 are respectively and fixedly arranged in the inner space of each quadrant, two power distribution modules 23 are fixedly arranged on the upper layer flip cover 21 corresponding to each group of battery modules 23, each power distribution module is provided with conductive copper bars, the upper layer flip cover 21 and two sides of the field-shaped metal frame 24 are rotatably connected through hinges, and when the upper layer flip cover 21 is turned down, the conductive copper bars can be communicated with the conductive copper bars on the power distribution modules 23 through screws, and the battery modules 25 and the external conductive bus bar are electrically connected; the flight control module 26 is fixed on the lower surface of the lower substrate 27, so as to facilitate maintenance of the cabin 3.
The upper layer edge substrate 22, the lower layer substrate 27 and the field-shaped metal framework 24 of the battery compartment 2 are stressed, and need to bear huge bending moment generated by the power module 1, the dead weight of the battery and the weight of a cabin and passengers, and have certain rigidity, and meanwhile, the field-shaped metal framework 24 needs to meet the requirement of light weight of an aircraft, so that the field-shaped metal framework 24 is made of aluminum alloy, magnesium aluminum alloy, carbon steel and the like, and the upper layer edge substrate 22 and the lower layer substrate 27 are made of carbon fiber composite materials. The design of the upper flip cover 21 also facilitates the taking and placing of the battery module 25.
The field-shaped metal framework 24 is composed of a framework side plate 241, a framework longitudinal beam 242, a framework cross beam 243 and a cross 244 which are arranged at the periphery, adopts the form of split parts, and is convenient for fixedly installing the cabin 3 below, a plurality of framework hangers 245 are uniformly arranged on the inner side surface of the framework side plate 241, so that the weights of the cabin 3 and passengers are uniformly distributed on the field-shaped metal framework 22, and meanwhile, the cabin structure of the cabin 3 can also strengthen the rigidity of the battery cabin 2; in order to facilitate the fixing of the battery module 25, the inner surface of the frame side plate 241 and the plurality of battery mounting positions 246 on the side surface of the cross 244 prevent the battery module 25 from shaking during the flight of the aircraft.
The seats are arranged in the cabin 3, the top surface of the cabin 3 is the lower surface of the battery compartment 2, and the landing gear 4 is symmetrically arranged on two sides of the cabin 3.
In the implementation process of the invention, the structural design is combined with finite element simulation analysis to simulate the rigidity of the battery compartment 2 under the condition of stress. And combining the result of finite element analysis, stacking the materials on a part with larger stress and a key energy transmission path as much as possible during design, and hollowing out the rest parts so as to achieve the aim of light weight.
The invention realizes the compatibility of long-time ascending and heavy loading on the power architecture and the structural layout of the multi-rotor manned aircraft, and has certain safety performance and attitude stability; the Y-shaped folding arm and the field-shaped metal framework are structurally designed, so that the requirements on structural compactness and mechanical properties are met, modular layout is achieved, maintenance is simple and convenient, and the engineering realization value is high.
It will be appreciated by persons skilled in the art that the foregoing description is a preferred embodiment of the invention, and is not intended to limit the invention, but rather to limit the invention to the specific embodiments described, and that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for elements thereof, for the purposes of those skilled in the art. Modifications, equivalents, and alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (3)
1. The battery compartment of the multi-rotor manned aircraft is characterized in that the battery compartment (2) comprises an upper layer flip cover plate (21), a framework upper layer edge substrate (22), a power distribution module (23), a field-shaped metal framework (24), a battery module (25), a flight control module (26) and a lower layer substrate (27); the upper layer flip cover plate (21) and the framework upper layer edge substrate (22) are arranged on the upper surface of the V-shaped metal framework (24), the lower layer substrate (27) is fixed on the lower surface of the V-shaped metal framework (24), the upper layer flip cover plate (21), the framework upper layer edge substrate (22), the V-shaped metal framework (24) and the lower layer substrate (27) enclose a four-quadrant inner space, four groups of battery modules (25) are respectively and fixedly arranged in the inner space of each quadrant, two power distribution modules (23) are fixedly arranged on the upper layer flip cover plate (21) corresponding to each group of battery modules (25), each power distribution module is provided with conductive copper bars, the upper layer flip cover plate (21) is rotatably connected with two sides of the V-shaped metal framework (24), and after the upper layer flip cover plate (21) is turned down, the conductive copper bars can be communicated with the conductive copper bars on the power distribution modules (23); the flight control module (26) is fixed on the lower surface of the lower substrate (27);
the V-shaped metal framework (24) is made of aluminum alloy, magnesium aluminum alloy or carbon steel;
the field-shaped metal framework (24) consists of a framework side plate (241), a framework longitudinal beam (242), a framework cross beam (243) and a cross (244) which are all detachably connected;
the inner side surface of the skeleton side plate (241) is uniformly provided with a plurality of skeleton hangers (245) for connecting the cabin (3);
and a plurality of battery mounting positions (246) are also arranged on the inner side surfaces of the framework side plates (241) and the cross (244).
2. The battery compartment of the multi-rotor unmanned aerial vehicle of claim 1, wherein the upper edge substrate (22) and the lower substrate (27) are each made of a carbon fiber composite material.
3. A multi-rotor manned aircraft, characterized in that the aircraft comprises the battery compartment of any one of claims 1-2, the aircraft further comprises a power module (1), a battery compartment (2), a cabin (3) and a landing gear (4), the power module (1) is directly connected with the battery compartment (2), and the power module and the battery compartment are arranged at the same height to form a flying platform; the cabin (3) is fixed below the battery cabin (2), and the landing gear (4) is arranged at the bottom of the cabin (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910391677.5A CN110155312B (en) | 2019-05-13 | 2019-05-13 | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910391677.5A CN110155312B (en) | 2019-05-13 | 2019-05-13 | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110155312A CN110155312A (en) | 2019-08-23 |
| CN110155312B true CN110155312B (en) | 2024-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910391677.5A Active CN110155312B (en) | 2019-05-13 | 2019-05-13 | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment |
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| Country | Link |
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| CN (1) | CN110155312B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116353832A (en) * | 2023-03-02 | 2023-06-30 | 之江实验室 | Light electric manned aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102126554A (en) * | 2011-01-28 | 2011-07-20 | 南京航空航天大学 | Unmanned air vehicle with multiple rotary wings in plane-symmetry layout |
| CN204871594U (en) * | 2015-06-10 | 2015-12-16 | 深圳九星智能航空科技有限公司 | Set up unmanned vehicles of removable battery in undercarriage |
| CN205150264U (en) * | 2015-10-30 | 2016-04-13 | 深圳高启科技有限公司 | Can dismantle unmanned aerial vehicle battery package assembly |
| WO2018024086A1 (en) * | 2016-08-01 | 2018-02-08 | 亿航智能设备（广州）有限公司 | Battery and aircraft |
| CN208360493U (en) * | 2018-06-11 | 2019-01-11 | 陕西飞猫无人机航空科技有限公司 | A kind of portable aerial survey quadrotor drone |
| CN210027900U (en) * | 2019-05-13 | 2020-02-07 | 之江实验室 | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment |
-
2019
- 2019-05-13 CN CN201910391677.5A patent/CN110155312B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102126554A (en) * | 2011-01-28 | 2011-07-20 | 南京航空航天大学 | Unmanned air vehicle with multiple rotary wings in plane-symmetry layout |
| CN204871594U (en) * | 2015-06-10 | 2015-12-16 | 深圳九星智能航空科技有限公司 | Set up unmanned vehicles of removable battery in undercarriage |
| CN205150264U (en) * | 2015-10-30 | 2016-04-13 | 深圳高启科技有限公司 | Can dismantle unmanned aerial vehicle battery package assembly |
| WO2018024086A1 (en) * | 2016-08-01 | 2018-02-08 | 亿航智能设备（广州）有限公司 | Battery and aircraft |
| CN208360493U (en) * | 2018-06-11 | 2019-01-11 | 陕西飞猫无人机航空科技有限公司 | A kind of portable aerial survey quadrotor drone |
| CN210027900U (en) * | 2019-05-13 | 2020-02-07 | 之江实验室 | Battery compartment of multi-rotor manned aircraft and manned aircraft comprising battery compartment |
Non-Patent Citations (1)
| Title |
|---|
| 一种无人多旋翼喷雾飞行器的设计;刘浩蓬;龙长江;胡奔;王坤殿;潘海兵;;华中农业大学学报(03);第140-144页 * |
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| CN110155312A (en) | 2019-08-23 |
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